Engineering Properties of IN-100 ALLOY INTERNATIONAL NICKEL CONTENTS Page COMPOSITION .................................................................................. 1 SPECIFICATION ................................................................................ 1 STRESS-RUPTURE PROPERTIES ............................................ 1 TENSILE PROPERTIES ........................................................... 1 HARDNESS ............................................................................. 1 PHYSICAL PROPERTIES ................................................................... 2 DENSITY ................................................................................ 2 MELTING RANGE .................................................................... 2 STABILITY .............................................................................. 2 THERMAL EXPANSION ............................................................ 2 ELECTRICAL RESISTIVITY ...................................................... 2 CHEMICAL PROPERTIES .................................................................. 2 OXIDATION RESISTANCE ....................................................... 2 Cyclic Test .................................................................... 2 Static Test .................................................................... 2 Dynamic Test ................................................................ 2 SULFIDATION RESISTANCE .................................................... 5 Crucible Test ................................................................ 5 Rig Test ........................................................................ 5 HEAT TREATMENT ........................................................................... 5 MECHANICAL PROPERTIES .............................................................. 5 TENSILE PROPERTIES ........................................................... 5 STRESS-RUPTURE PROPERTIES ............................................ 5 STRESS-RUPTURE PARAMETER ............................................ 8 CREEP RATE .......................................................................... 8 MINIMUM CREEP RATE ........................................................... 8 DYNAMIC MODULUS OF ELASTICITY ...................................... 8 IMPACT PROPERTIES ....................................................................... 11 HOT HARDNESS ............................................................................... 11 FATIGUE .......................................................................................... 11 MECHANICAL ......................................................................... 11 THERMAL ............................................................................... 14 MACHINING AND GRINDING ............................................................. 14 APPENDIX ........................................................................................ 16 REFERENCES ................................................................................... IBC Engineering Properties of IN-100 ALLOY IN-100 alloy* is a nickel-base precipitation refractory metal content make IN -100 particularly hardenable, vacuum cast alloy possessing high attractive on a strength to density basis. The rupture strength through 1900 ºF. The high per- alloy has been successfully cast and utilized in a centages of aluminum and titanium and the low variety of shapes from turbine blades, vanes and nozzles to integral wheels. COMPOSITION – WEIGHT PER CENT Element Nominal Range (AMS 5397) Carbon 0.18 0.15 – 0.20 Chromium 10.00 8.00 – 11.00 Cobalt 15.00 13.00 – 17.00 Molybdenum 3.00 2.00 – 4.00 Titanium 4.70 4.50 – 5.00 Aluminum 5.50 5.00 – 6.00 Vanadium 0.90 0.70 – 1.20 Zirconium 0.06 0.03 – 0.09 Boron 0.014 0.01 – 0.02 Iron LAP** 1.00 max. Manganese LAP 0.20 max. Silicon LAP 0.20 max. Sulfur LAP 0.015 max. Nickel balance (60) balance SPECIFICATION The AMS 5397 specification for IN-100 alloy requires the following mechanical properties in the as-cast condition: Stress - Rupture Properties – Minimum Test Temp. Stress Life E long. ºF psi Hrs. % in 4D 1800 29,000 23 4 Tensile Properties – Minimum 0.2% Yield Tensile Test Temp. Elong. Strength Strength ºF % in 4D psi psi 70 95,000 115,000 5 Hardness Rockwell C 30-44 or equivalent There are many alternate specifications in existence and individual companies should be contacted as to their requirements. * U.S. Patent #3,061,426; produced under license from The International Nickel Company, Inc. **Low as possible 1 PHYSICAL PROPERTIES Density 0.280 lb./cu. in. (7.75 g/cu. cm) Melting Range 2305 - 2435 ºF (1260 -1335 ºC) Stability While long-time elevated temperature stability can be demonstrated only by long-time exposure, a mathematical analysis based on electron vacancy concentration (see Appendix) is useful in indicating the susceptibility of an alloy to form sigma. The electron vacancy number, Nv , of IN-100 of nominal composition is 2.46. Nv values over 2.50 generally indicate that an alloy is susceptible to sigma. When IN-100 was originally introduced, the suggested range for titanium extended from 4.5 to a max- imum of 5.5 per cent. Compositions toward the top side of this range did exhibit sigma formation. For example, a 5.3 Ti alloy with an Nv of 2.70 contained sigma which detracted from rupture life. The maximum titanium level then was reduced to the current AMS specification value of 5.0 percent. This change eliminated the deleterious effects of sigma on material properties without sacrificing any of the material's desired properties. Thermal Expansion (See Figure 1) Mean Mean Test Temp. Coefficient Test Temp. Coefficient oF per oF oF per oF 70 - 200 7.2 x 10-6 70 – 1200 8.0 x 10-6 70 - 400 7.2 70 – 1400 8.3 70 - 600 7.3 70 – 1600 8.8 70 - 800 7.5 70 – 1800 9.3 70 - 1000 7.7 70 – 2000 10.1 Electrical Resistivity 143.0 microhm-cm at R.T. CHEMICAL PROPERTIES OXIDATION RESISTANCE Cyclic Test (See Figure 2) Samples were given a cyclic exposure by heating in air at 1900 ºF for 16 hours and then cooling for 8 hours. Alloy Wt. Change, % in 208 Hrs. IN -100 –.80 Alloy 713LC –.10 Static Test (See Figure 3) The static oxidation tests, performed by General Electric, were conducted by placing specimens in open zircon cup-type crucibles and oxidizing them in the static atmosphere of electric box furnaces.(1) Dynamic Test (See Figure 4) The dynamic oxidation tests were performed by General Electric in a natural gas-fired flame tunnel. Test specimens were placed in a rotating fixture positioned in the hot zone of the flame tunnel perpendicular to the gas flow.(1) 2 Figure 1. Thermal – Expansion of IN-100 Alloy. Figure 2. Oxidation Resistance of IN-100 Alloy. and 713C: Cyclic Test 16 Hours At 1900 ºF, Cool In Air For 8 Hours. Figure 3. Comparison of Oxidation Kinetics of IN-100 and Alloy 713C at 1600 and 2000 ºF. Note the Decreasing Oxidation Rates at 2000 ºF (t>100 min.). 3 Figure 4(a). Weight Change During Oxidation In High Velocity Natural Gas Combustion Products at 1600 ºF. Figure 4(b). Weight Change During Oxidation In High Velocity Natural Gas Combustion Products at 2000 ºF. Figure 4(c). Sulfidation Resistance of Nickel Base Alloys In A Com- bustion Rig Test. Reference: Quarterly Progress Report No. 1 (July-Sept. 1966) "Study of the Hot Corrosion of Superalloys" by Lycoming Division of AVCO Corp. under Air Force contract AF33(615)-5212, Project No. 7381. 4 SULFIDATION RESISTANCE Crucible Test – 90% Na2SO4/10% NaCl 1700 ºF Alloy Wt. Loss, % in 1 Hr. Wt. Loss, % in 2 Hrs. IN-100 0 2 Alloy 713 LC 12.8 13 IN -162 0 14 Rig Test (See Figure 4(C)) Paddle specimens with an airfoil configuration were rotated in and out of a furnace fired with JP-4 fuel (.04 w/o S) for 120 hours on a cyclic basis. During the heating cycle, a controlled amount of synthetic seawater was sprayed into the combustion exit and mixed with the gas stream. The tempera- ture profile on the airfoil ranged from 1600-1750 ºF with the maximum on the trailing edge. HEAT TREATMENT The properties shown in this bulletin are for IN- a partial solutioning. If the coating is to be dif- 100 in the as-cast condition. In many applications, fused at 1900-1950 ºF, it is suggested that the IN-100 components are given a protective coating material receive a preliminary high temperature to enchance corrosion resistance. This treatment solutioning at 2100-2150 ºF. An aging treatment at generally includes a diffusion cycle at a 1500-1600 ºF is recommended after the coating temperature between 1800-2100 ºF for 2-8 hours. cycle. This should provide material with a In effect, this treatment provides the material with capability of maintaining a consistently high level of mechanical properties. MECHANICAL PROPERTIES Tensile Properties (See Figure 5) Test 0.2% Yield Tensile Temp. Strength Strength Elong. Reduction ºF psi psi % of Area 70 123,000 147,000 9.0 11.0 1000 128,000 158,000 9.0 11.0 1200 129,000 161,000 6.0 7.0 1350 127,000 159,000 6.5 7.2 1500 118,000 144,000 6.0 7.2 1700 73,000 107,000 6.0 7.2 1900 41,000 64,000 6.0 8.0 Creep – Rupture Properties Coarse grain (≥1/8") and fine grain (≤1/16") castings have exhibited nearly identical creep rupture properties. These are summarized as follows: Stress – Rupture Properties (See Figures 6 and 7 and raw data in Table I) Test Stress, psi, for Rupture in Temp. ºF 10 Hr. 100 Hr. 1,000 Hr. 1350 - 97,000 83,000 1500 90,000 73,000 55,000 1700 52,000 38,000 25,000 1800 38,000 25,000 15,000 1900 - 16,000 8,500 5 Figure 5. Typical Tensile Properties